Numerical investigation of supersonic turbulent boundary layers along forward- and backward-facing compression ramps

用大涡模拟(LES)方法研究了壁面剪切流激波-湍流相互作用的高级模拟问题，采用亚格子尺度近似反卷积方法。在与新西伯利亚RAS理论和应用力学研究所的现有密切合作框架内，提供了所考虑的流动构型的详细和高质量的实验数据。讨论了STBL流场中非定常大尺度结构的存在和机理，以及它们对于可靠地预测气动和热力学流动特性的意义，这是目前标准湍流模型所不能令人满意的。在复杂性的逐步增加中，我们首先考虑在马赫数为2.9时的25°压缩斜坡，然后是在相同马赫数下的25°压缩-25°解压缩构型。我们期望该项目的结果是对(I)激波和分离动力学，(Ii)大尺度非定常流动结构(类Görtler涡)，(Iii)可压缩性效应的重要性，(Iv)如何改进标准湍流模型的方法有了明确的了解。

The problem of advanced modeling of shock-turbulence interaction for wall-bounded shear flows (STBL) is investigated by Large-Eddy Simulation (LES) using the Approximate Deconvolution Method for subgrid-scale modeling. Detailed and high-quality experimental data for the considered flow configurations are available in the framework of an existing close cooperation with the Institute of Theoretical and Applied Mechanics, RAS, Novosibirsk. Open questions addressed are the existence and mechanisms of unsteady large-scale structures in the STBL flow fields and their significance for a reliable prediction of aerodynamic and thermodynamic flow properties which is unsatisfactory with present standard turbulence models. In a stepwise increase of complexity, we first consider a 25°-compression ramp at Mach 2.9, followed by a 25°-compression -25°-decompression configuration at the same Mach number. We expect that as result of the project a clear understanding of (i) shock and separation dynamics, (ii) large-scale unsteady flow structures (Görtler-like vortices), (iii) significance of compressibility effects, (iv) approaches on how to improve standard turbulence models is achieved.